重力梯度稳定小卫星的最优主动磁控和动量轮控制  

An Optimal Control Algorithm of a Gravity Gradient Stabilized Small Satellite with Momentum Wheel and Magnetic Torque

作　　者：黄卫东[1] 张育林[1] 

机构地区：[1]国防科学技术大学,长沙410073

出　　处：《航天控制》2005年第4期27-31,共5页Aerospace Control

摘　　要：为了提高小卫星定点精度,姿态控制系统采用俯仰轴动量轮控制和三轴磁力矩控制。用四元数方法建立起卫星动力学方程和运动学方程。以响应时间和响应时间内欧拉角误差和角速率误差的平方和这两个单目标作为目标函数,以三轴的位置增益、速率增益和卸载增益为设计变量,以三轴欧极子矩不超过要求值,俯仰轴的轮动量矩不超过要求值,以及末尾响应时间内应保证欧拉角和角速率逼近控制值为约束条件,建立起卫星最优控制模型。最后,作为例子应用到小卫星姿态控制中,结果证实最优控制算法是可行有效的。与传统PD控制相比,优化后的姿态控制性能也大大提高。In order to improve the pointing accuracy of small satellite, the attitude control system is controlled with pitch-axis momentum and three-axis magnetic torque. The satellite dynamics equation and kinematic equations are built with the method of quaternion. Magnetic torque generates magnetic dipole moments whose interactions with the earth＇s magnetic field produce the torque necessary to remove the excess momentum. Three position, three rate, and a dumping control gains are optimaUy found by building up the optimal attitude control model. In the model, two single objectives： the minimum of the transient time and the minimum of the sum of both the square sum of the attitude angle error and the square sum of the angle rate error are integrated into the multi objectives with multiobjective optimization approach. The constraints require that the attitude angle, the angle rate, the three-axis dipole moment and the pitch wheel momentum should not exceed the required value. Finally, an application to the attitude control of small satellite is presented as an example. Results show that the optimal control algorithm is feasible, effective and reliable, and attitude control performance is also significantly improved after optimization, compared with the traditional PD control.

关 键 词：姿态控制 优化控制 PID控制 多目标优化 

分 类 号：V448[航空宇航科学与技术—飞行器设计]